• Proceedings of the Korean Society For Composite Materials Conference
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• 2005.11a
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• pp.215-218
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• 2005

In this research, design scheme of fiber Bragg grating(FBG) sensor system for aircraft application is suggested from the results and the know-how from the fon11er researches on structural health monitoring techniques using fiber optic sensors. Design factors to be taken into consideration were derived for both sensor parts including connection and system parts. For the stability of FBG sensor system, design requirements of temperature, vibration, humidity, electromagnetic interference were presented from U. S. military standards. The direction of software programming which increases stability and perfon11ance of the aircraft with the FBG sensor system was also examined.

• Journal of the Korean Society of Manufacturing Process Engineers
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• v.19 no.2
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• pp.103-110
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• 2020

Riveting is mainly used to assemble the aircraft fuselage. An average of 2~3 workers is needed to assemble an aircraft fuselage consisting of various size frames by riveting. In this study, a riveting process that enables one-person operation using an automated C-frame riveting machine was proposed for improving the efficiency of productivity. The proposed process was verified stability through structural analysis. In the range that can maintain structural stability, panel thickness of the riveting machine and shape were modified to optimizing the shape for reducing the weight of the riveting process. The structural analysis was performed by software ANSYS workbench 19.2. The optimized riveting machine was reduced by 257kg compared to the existing model.

• Advances in aircraft and spacecraft science
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• v.10 no.6
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• pp.545-554
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• 2023

The widespread introduction of unmanned aircrafts has led to the understanding of the need to organize a common information space for manned and unmanned aircrafts, which is reflected in the Russian Unmanned aircraft system Traffic Management (RUTM) project. The present article deals with the issues of spatial information database (DB) organization, which is the core of RUTM and provides storage of various data types (spatial, aeronautical, topographical, meteorological, vector, etc.) required for flight safety management. Based on the analysis of functional capabilities and types of work which it needs to ensure, the architecture of spatial information DB, including the base of source information, base of display settings, base of vector objects, base of tile packages and also a number of special software packages was proposed. The issues of organization of these DB, types and formats of data and ways of their display are considered in detail. Based on the analysis it was concluded that the optimal construction of the spatial DB for RUTM system requires a combination of different model variants and ways of organizing data structures.

• Journal of the Korean Society for Aviation and Aeronautics
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• v.24 no.2
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• pp.68-73
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• 2016

2016, in total 53 corporations operate 160 aircraft. Since 2000, 52 accidents occurred in these corporations. This number takes 20.2% out of in total 257 accidents. Especially in 2016, in two(2) accidents, two(2) aircraft and people onboard were damaged. According to accident reports of aircraft using service, in most cases actions against common sense were connected to accidents. This means that attentions of managers or pilot would have protected accidents. On the basis of such background, this research analyses accidents cases of corporations operating aircraft by utilizing ahp. According to this anlysis, unlike scheduled and unscheduled airlines, pilots in command (0.109) and assisting crew (0.105) in Liveware have taken the most importance. Operational procedure (0.100) in Software and a controlling system (0.086) in Hardware have shown the second most importance. This result demonstrates that in case of corporations operating aircraft require safety management at different level than airlines.

• Advances in aircraft and spacecraft science
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• v.8 no.4
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• pp.303-330
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• 2021

The paper discusses the effect of the winglets on the aerodynamic and aeroacoustic performance of Boeing 737-800 aircraft by numerical approach. For this purpose, computational fluid dynamics and fluent commercial software are used to solve the compressible flow governing equations. The RANS method and the K-ω SST turbulence model are selected to simulate the subsonic flow around the wing with acceptable accuracy and low computational cost. The main variables of steady flow around the simple and blended wing in constant atmospheric conditions are computed by numerical solution of governing equations. The solution of the acoustic field has also been accomplished by the broad-band acoustic source model. The results reveal that adding a blended winglet increases the pressure difference near the wingtip,which increases the lift force. Also, the blended winglet reduces the power and magnitude of vorticities around the wingtip, which reduces the wing's drag force. The effects of winglets on aerodynamic forces lead to a 3.8% increase in flight range and a 3.6% increase in the maximum payload of the aircraft. Also, the acoustic power level variables on the surfaces and fields around the wing have been investigated integrally and locally.

• Journal of Advanced Navigation Technology
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• v.15 no.5
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• pp.687-695
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• 2011

The defect caused by the software industry that is the source of knowledge-centric, information-centric and technology-centric affects an engine which operate a major role for operation of aircraft. Therefore, we should minimize the danger from the defect by strengthening the stability of aviation through the stability analysis of software. In this paper, we examine the laws and systems about the aircraft defects and software safety and propose the enhancement and the enactment of the law or measures to strengthen aviation safety. We should the existing law or system as items, such as the revision related to the safety analysis, standards of quality assurance including safety, application of quality assurance that you must attach the safety analysis report, assessment of detailed instructions of certification authorities. In addition, we should enact the new law and system as items such as the mandatory software evaluation and certification, continuous assessment based on the software life cycle, mandatory introduction of a standardized development methodology, strengthening of advanced workforce system. We can expect the improvement of software quality and an enhanced aviation safety by improving existing laws or systems and enacting new laws or systems.

• Journal of Aerospace System Engineering
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• v.17 no.1
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• pp.33-41
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• 2023

As seen in the case of the Boeing 737 Max accident, the proportion of aircraft software is rapidly increasing. However, it is vulnerable to safety issues. In case of domestic aircraft software, to operate a Light Unmanned Aerial Vehicle (LUAV) less than an empty weight of 150 kg, safety certification is required for an Ultra-Light Vehicle (ULV). However, software certification procedure is not included. Since the use of LUAVs has increased recently, software verification is required. This paper proposed a checklist of LUAV software that could be applied to LUAV referring DO-178C, an aviation software certification standard. A case study of applying the proposed checklist to the Model-based Development-based Helicopter Flight Control Computer (FCC) project currently used by domestic and foreign advanced companies and institutions was conducted.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.47 no.7
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• pp.535-540
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• 2019

The coupling between different models for MDO (Multi-disciplinary Optimization) greatly increases the complexity of the computational framework, while at the same time increasing CPU time and memory usage. To overcome these difficulties, POD (Proper Orthogonal Decomposition) and RBF (Radial Basis Function) are used to solve the optimization problem of determining the thickness of composites and sandwich cores when composite sandwich structures are used as aircraft wing skin materials. POD and RBF are used to construct surrogate models for the wing shape and the load data. Optimization is performed using the objective function and constraint function values which are obtained from the surrogate models.

• Journal of Korean Society for Quality Management
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• v.41 no.3
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• pp.433-441
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• 2013

Purpose: This study investigates software qualification procedures based on the FA-50 flight control software to satisfy high reliability and flight safety. Methods: We studied software qualification categories, standard/specification and developed country case. We proposed procedure to satisfy not only flight safety but also international standard. Results: The proposed software qualification procedure satisfied flight safety and airworthiness based on the testing result of the FA-50 flight control software. Conclusion: This paper showed an appropriate qualification procedures of the flight control software in domestic circumstance through the FA-50 flight control software qualification.

• 제어로봇시스템학회:학술대회논문집
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• 2001.10a
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• pp.156.6-156
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• 2001

A computer software system which enables to assess the air combat performance only by a computer is currently under development. The system is composed with plural aircraft models, missile models, bullet models etc. The aircraft can implement several empirical air combat maneuvers automatically depending on the situation , therefore air combat simulations and assessment can be attained. Some of these maneuvers and features are explained.